CN113232840B - Tail-sitting vertical type vertical take-off and landing aircraft adopting series-parallel landing gear - Google Patents
Tail-sitting vertical type vertical take-off and landing aircraft adopting series-parallel landing gear Download PDFInfo
- Publication number
- CN113232840B CN113232840B CN202110612864.9A CN202110612864A CN113232840B CN 113232840 B CN113232840 B CN 113232840B CN 202110612864 A CN202110612864 A CN 202110612864A CN 113232840 B CN113232840 B CN 113232840B
- Authority
- CN
- China
- Prior art keywords
- tail
- aircraft
- control system
- landing
- parallel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000005259 measurement Methods 0.000 claims description 4
- 230000033001 locomotion Effects 0.000 abstract description 15
- 210000001503 joint Anatomy 0.000 abstract 1
- 230000005484 gravity Effects 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a tail sitting vertical take-off and landing aircraft adopting series-parallel landing gears, belonging to the technical field of aviation, comprising an aircraft body, wings, a power system, series-parallel two-degree-of-freedom landing gears and parallel two-degree-of-freedom landing gears, wherein the series-parallel two-degree-of-freedom landing gears and the parallel two-degree-of-freedom landing gears are distributed on the lower two sides of the aircraft body, the tail sitting vertical take-off and landing aircraft can actively control the angle between the aircraft body and the series-parallel two-degree-of-freedom landing gears and the angle between the aircraft body and the series-parallel two-degree-of-freedom landing gears to carry out variant motion of the landing gears in a split and butt joint mode, the series-parallel landing gears are arranged on the basis of simple structure, contact points between the tail sitting vertical take-off and landing aircraft and the ground are increased, so that the take-off and landing stability is improved, meanwhile, the aircraft tail is in a sitting vertical type vertical take-off and landing aircraft with effective ground movement capability by matching with the variant movement of the landing gear.
Description
Technical Field
The invention belongs to the technical field of aviation, relates to a tail sitting vertical type vertical take-off and landing aircraft, and relates to a tail sitting vertical type vertical take-off and landing aircraft adopting series-parallel type landing gears.
Background
The thrust direction of the tail sitting type aircraft is fixed on the longitudinal axis of the aircraft body, the tail sitting type aircraft takes off, the aircraft is rotated into flat flight after reaching a certain height, the aircraft climbs firstly when landing, the aircraft nose faces upwards, and then the thrust is reduced to land vertically. When the thrust reversing is realized, the thrust and the machine body rotate synchronously.
The tail-seated vertical aircraft is taken as a popular direction in the research field of the domestic vertical take-off and landing fixed wing aircraft, and along with the existing research history of decades, part of key problems are still not solved at present, a mature model is not formed, the take-off and landing stability of the tail-seated vertical aircraft is poor due to the fact that the aircraft body is vertical, and the fixed landing gear adopted by the currently-proposed testing machine or civil aircraft is blank for the development of land-air dual-purpose landing gear technology with ground movement capability, and take-off and landing constraints become one of key technologies for restricting the development of the tail-seated vertical aircraft.
In the prior art, a patent document with publication number CN109911182A discloses a retractable tail boom landing gear of a tail sitting type vertical take-off and landing aircraft, which is composed of a tail sitting type vertical take-off and landing aircraft, a main landing gear, a tail boom, a supporting rod, a tail boom driving mechanism and a supporting rod driving mechanism, wherein the tail boom supporting mechanism and the supporting rod driving mechanism are symmetrically installed on two sides of an aircraft body and used for driving the tail boom and the supporting rod to open and close, the retractable tail boom landing gear plays a supporting role when the aircraft is parked on the ground, and plays a role in operating and balancing the aircraft in a horizontal flight state of the aircraft. Although the invention relates to the landing gear structure variant technology primarily, the landing gear can be retracted, the landing gear main body structure is a straight section type structure, the capability of balancing and auxiliary operation is poor due to the structural weight of the landing gear, the landing gear is a wheel type landing gear, the landing stability is poor, and the landing gear does not have the self-adaptive landing capability, and meanwhile, due to the existence of the wheel type main landing gear, although the aircraft and the ground have 6 contacts, when the aircraft is moved by the single-side landing gear, the sliding friction of the wheel type main landing gear cannot ensure that the aircraft is easy to tip over due to the movement of the single-side landing gear.
Disclosure of Invention
The invention provides a tail-sitting vertical take-off and landing aircraft adopting series-parallel landing gears, aiming at solving the technical problems, the invention provides the following technical scheme: a tail-sitting vertical type vertical take-off and landing aircraft adopting series-parallel landing gears comprises an aircraft body, wings, a power system, series two-section landing gears and parallel two-degree-of-freedom landing gears;
the tandem type two-section undercarriage and the parallel type two-degree-of-freedom undercarriage are symmetrically arranged on the upper side and the lower side of the wing, and are divided into two single groups and symmetrically arranged on the wing on the left side and the right side of the fuselage;
the single group of the tandem type two-section undercarriage comprises a first support rod control system, a first support rod, a first tail support rod control system and a first tail support rod which are sequentially hinged; the first support rod control system is installed on one side of the wing, and the first support rod control system and the first tail support rod control system are used for adjusting the relative angle and the form between the tandem type two-section undercarriage and the airplane body;
the single group of the parallel two-degree-of-freedom undercarriage comprises a second supporting rod control system, two second supporting rods, two second tail supporting rod control systems, two second tail supporting rods, a tail supporting vertical tail wing and a tail supporting horizontal tail wing, the second supporting rod control system is arranged at the other side of the wing, the top ends of the two second supporting rods are hinged with the wing through the second supporting rod control system, the tail ends of the two second supporting rods are respectively provided with a second tail supporting rod control system, the top ends of the two second tail supporting rods are respectively hinged with the tail end of one second supporting rod through one second tail supporting rod control system, the tail ends of the two second tail stay bars are hinged and provided with tail stay vertical tail wings, the tail stay horizontal tail wings are arranged between the tail stay vertical tail wings at the left side and the right side of the machine body, and the second support rod control system and the second tail support rod control system are used for adjusting the relative angle and the form between the parallel two-degree-of-freedom undercarriage and the aircraft body.
Preferably, an aileron is mounted on the wing.
Preferably, the airplane wheel is further included, and the airplane wheel is connected with the tail end of the second tail boom rod and symmetrically arranged on the left side and the right side of the vertical tail wing of the tail boom.
Preferably, the first supporting rod control system, the first tail supporting rod control system, the second supporting rod control system and the second tail supporting rod control system are all provided with a single chip microcomputer, the single chip microcomputer is in wireless connection with the laser ranging unit and the inertia measuring unit, and the laser ranging unit and the inertia measuring unit are arranged on the wing.
Has the advantages that:
1. the series-parallel series-parallel landing gear is innovatively adopted, the landing gear plays a supporting role when the aircraft is parked on the ground, the landing gear can be folded when the aircraft is in a cruise state of rotating and flying horizontally, the two-section unfolded landing gear and the two-degree-of-freedom parallel landing gear are finally combined, and the landing gear in the horizontal state reduces additional resistance brought by the structure.
2. The main body is positioned at the tail part of the aircraft body, the tail boom vertical tail wing and the tail boom horizontal tail wing are far away from the gravity center of the aircraft, the force arm for balancing and operating is long, the operating capability is strong, the balancing additional resistance is small, the control capability and the flight efficiency of the aircraft during flight are improved, and the problem that the existing tail sitting type vertical take-off and landing aircraft is difficult to vertically balance in the horizontal flight stage due to the fact that the arrangement of the non-horizontal tail wings is adopted in order to reduce the distance between the gravity center of the aircraft and the ground and improve the stability of the aircraft supported on the ground and in the take-off and landing processes is effectively solved.
3. When the vertical take-off and landing aircraft is in mode conversion and landing, the landing gear which is symmetrically controllable can be subjected to self-adaptive auxiliary trim adjustment and landing, and the take-off and landing stability of the vertical take-off and landing aircraft and the adaptability to task work in a future complex environment are enhanced.
4. The landing gear of series-parallel connection formula has increased the vertical VTOL aircraft of tail seat when taking off and land the contact point with ground on the basis that remains simple structure, has not only improved the stability of taking off and land, simultaneously through the variant motion of cooperation landing gear for the vertical VTOL aircraft of tail seat has possessed effectual ground mobility.
5. The series-parallel connection type undercarriage two-side asymmetric structure brings convenience to the balance of the aircraft with the asymmetric fuselage structure and the tail sitting vertical take-off and landing aircraft in the transition state from vertical take-off and landing/hovering to cruising.
Drawings
FIG. 1 is a schematic view of a ground parking structure according to the present invention;
FIG. 2 is a schematic view of the position of the first and second strut control systems on the wing according to the present invention;
FIG. 3 is a schematic view of an aerial cruise elevation configuration of the present invention;
FIG. 4 is a schematic view of the aerial cruise overhead structure of the present invention;
FIG. 5 is a schematic view of the tandem two-stage landing gear adduction self-adaptive landing state of the present invention;
FIG. 6 is a schematic view of the tandem two-stage landing gear of the present invention in an extended self-adaptive landing state;
FIG. 7 is a schematic diagram of the ground movement status according to the present invention;
the symbols in the drawings illustrate that: 1: a body; 2: an airfoil; 3: a power system; 4: a tandem two-section undercarriage; 5: a parallel two-degree-of-freedom undercarriage; 401: a first strut control system; 402: a first support bar; 403: a first tail boom control system; 404: a first tail stay bar; 501: a second strut control system; 502: a second support bar; 503: a second tail boom control system; 504: a second tail stay; 505: a tail boom vertical tail; 506: a tail boom horizontal rear wing; 6: an aileron; 7: a wheel.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific preferred embodiments.
In the description of the present invention, it is to be understood that the terms "left side", "right side", "upper part", "lower part", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and that "first", "second", etc., do not represent an important degree of the component parts, and thus are not to be construed as limiting the present invention. The specific dimensions used in the present example are only for illustrating the technical solution and do not limit the scope of protection of the present invention.
Example 1:
referring to fig. 1-2, the invention provides a technical scheme, namely a tail-landing vertical take-off and landing aircraft adopting series-parallel landing gears, which comprises a fuselage 1, wings 2, a power system 3, series two-section landing gears 4 and parallel two-degree-of-freedom landing gears 5; the tandem type two-section undercarriage 4 and the parallel type two-degree-of-freedom undercarriage 5 are symmetrically arranged on the upper side and the lower side of the wing 2, and the tandem type two-section undercarriage 4 and the parallel type two-degree-of-freedom undercarriage 5 are divided into two single groups and symmetrically arranged on the wing 2 on the left side and the right side of the fuselage 1; a single set of tandem two-section landing gear 4 comprises a first strut control system 401, a first strut 402, a first tail strut control system 403 and a first tail strut 404, all of which are articulated in sequence; the first strut control system 401 is installed on one side of the wing 2, and the first strut control system 401 and the first tail strut control system 403 are used for adjusting the relative angle and the form between the tandem type two-section landing gear 4 and the fuselage 1; the single group of the parallel two-degree-of-freedom undercarriage 5 comprises a second supporting rod control system 501, two second supporting rods 502, two second tail supporting rod control systems 503, two second tail supporting rods 504, a tail supporting vertical tail wing 505 and a tail supporting horizontal tail wing 506, wherein the second supporting rod control systems 501 are installed on the other side of the wing 2, the top ends of the two second supporting rods 502 are hinged with the wing 2 through the second supporting rod control systems 501, the tail ends of the two second supporting rods 502 are respectively provided with the second tail supporting rod control systems 503, and the top ends of the two second tail supporting rods 504 are respectively hinged with the tail end of one second supporting rod 502 through one second tail supporting rod control system 503; the single group of second support rod control system 501, the two second support rods 502, the two second tail support rod control systems 503 and the two second tail support rods 504 form a movable parallelogram structure; the tail ends of the two second tail stay rods 504 are hinged and provided with tail stay vertical tail wings 505, tail stay horizontal tail wings 506 are arranged between the tail stay vertical tail wings 505 on the left side and the right side of the machine body 1, and a second stay rod control system 501 and a second tail stay rod control system 503 are used for adjusting the relative angle and the form between the parallel two-degree-of-freedom undercarriage 5 and the machine body 1; the motion enveloping body of the power system 3 is not overlapped with the variant motion enveloping bodies of the tandem type two-section undercarriage 4 and the parallel type two-degree-of-freedom undercarriage 5, the power system 3 is of a propeller structure, and power driving structures are arranged in the first supporting rod control system 401, the first tail supporting rod control system 403, the second supporting rod control system 501 and the second tail supporting rod control system 503 and can drive the connected structures to rotate; before taking off and after landing, the tail sitting type vertical take-off and landing aircraft is supported on the surface of a take-off or parking area through a series two-section undercarriage 4 and a parallel two-degree-of-freedom undercarriage 5, and the main weight of the tail sitting type vertical take-off and landing aircraft is borne and the attitude balance is kept;
furthermore, the wings 2 are provided with ailerons 6, which are beneficial to matching with the tail boom horizontal tail wing 506 to adjust and adapt to the airflow direction.
Further, the airplane wheel 7 is further included, and the airplane wheel 7 is connected with the tail end of the second tail stay 504 and symmetrically arranged on the left side and the right side of the tail stay vertical tail wing 505.
Further, the first support rod control system 401, the first tail support rod control system 403, the second support rod control system 501 and the second tail support rod control system 503 are all provided with a single chip microcomputer, the single chip microcomputer is wirelessly connected with the laser ranging unit and the inertia measurement unit, the laser ranging unit and the inertia measurement unit are arranged on the wing and can measure corresponding data, the data are wirelessly transmitted to the single chip microcomputer, and the single chip microcomputer controls the brake force driving structure to drive the first support rod 402, the first tail support rod 404, the second support rod 502 and the second tail support rod 504 to move.
Example 2:
referring to fig. 3-4, on the basis of embodiment 1, when the present invention enters a flight state, the first strut control system 401 and the first tail strut control system 403 respectively control the first strut 402 and the first tail strut 404 to rotate, so that the first strut and the first tail strut perform attitude adjustment with respect to the fuselage 1, gradually close, and maintain a horizontal state to reduce resistance; the second supporting rod control system 501 and the second tail supporting rod control system 504 respectively control the second supporting rod 502 and the second tail supporting rod 504 to rotate for attitude adjustment, the tandem type two-section undercarriage 4 and the parallel type two-degree-of-freedom undercarriage 5 can assist the balance of the whole device, the tail supporting horizontal tail wing 506 and the aileron 5 are matched to adjust the adaptive airflow direction, aerodynamic force beneficial to the flight of the airframe 1 is generated, after the whole device is stabilized, the undercarriage is closed, the distance between the tail supporting vertical tail wing 505 and the tail supporting horizontal tail wing 506 and the gravity center of the aircraft is far away, the moment arm for balance and control is long, the control capability is strong, the balance additional resistance is small, and the control capability and the flight efficiency of the aircraft during flight are improved.
The tandem type two-section undercarriage 4 and the parallel type two-degree-of-freedom undercarriage are positioned at the tail end of the airframe 1, the distance between the tail support horizontal tail wing 506 and the gravity center of the tail sitting type vertical take-off and landing aircraft is the sum of the lengths of the second support rod 502 and the second tail support rod 504, and the length parameters of the second support rod 502 and the second tail support rod 504 need to ensure that the tail support horizontal tail wing 506 has good operation performance.
Example 3:
referring to fig. 5 to 6, on the basis of embodiment 1, when the aircraft enters a ground parking state from a flight state, the tail-mounted vertical take-off and landing aircraft first enters an air hovering state, a laser ranging unit measures a distance value of the aircraft body from the ground, then data is transmitted to a single chip microcomputer arranged in each control system, then a first support rod control system 401 and a first tail support rod control system 403 respectively control a first support rod 402 and a first tail support rod 404 to rotate, so that the tandem type two-section undercarriage 4 is expanded, attitude adjustment is performed on the tandem type two-section undercarriage 4 relative to the aircraft body 1, the tandem type two-section undercarriage and a corresponding landing ground are adjusted to a proper height, and a second support rod control system 501 and a second tail support rod control system 504 respectively control a second support rod 502 and a second tail support rod 504 to rotate, so that the parallel type two-degree-of-freedom undercarriage 5 is expanded to perform attitude adjustment; the cooperation of tail boom horizontal tail 506 and aileron 5 is adjusted and is adapted the air current direction, produce the aerodynamic force that helps fuselage 1 flight, the overall stability of being convenient for descends, make first tail vaulting pole 404 and second tail vaulting pole 504 and ground contact and then support fuselage 1, the inertia measuring unit detects simultaneously, overall structure whether inclines, whether be in stable condition, will detect data transmission to singlechip, control serial-type two-section undercarriage 4 and parallel two-degree-of-freedom undercarriage 5, adjust its state and descend regional environment and cooperate, thereby realize the self-adaptation and descend.
Example 4:
referring to fig. 7, on the basis of embodiment 1, when the tail-sitting type vertical take-off and landing aircraft is on the ground and needs to move, the variant motion of the tandem two-section landing gear 4 provides forward or backward power for the tail-sitting type vertical take-off and landing aircraft, and also can realize direction deflection in the process of moving the ground, the structures of the single group of the tandem two-section landing gear 4 on the left and right sides of the wing 2 cooperate to move, the first support rod control system 401 controls the first support rod 402 to rotate, the first tail support rod control system 403 controls the first tail support rod 404 to move on the ground like a human leg, and the two single groups cooperate to realize the movement of the tail-sitting type vertical take-off and landing aircraft; in order to prevent the tail sitting type vertical take-off and landing aircraft from tipping or being worn with the ground in the movement process of the tandem type two-section landing gear 4, the tail end of the second tail stay 504 is provided with the airplane wheels 7 which are symmetrically arranged at the left side and the right side of the tail stay vertical tail wing 505, in the movement process, the airplane wheels 7 are in contact with the ground, and the second tail stay 504, the second tail stay control system 503 and the second support rod 502 are in a ground-off state, so that the integral movement is convenient, and the friction is reduced; when the tandem type two-section undercarriage 4 deflects in the attitude or movement direction of the tail-sitting vertical take-off and landing aircraft, the second tail stay 504, the second tail stay control system 503 and the second support rod 502 are in a ground-contacting state, so that the support points between the whole structure and the ground are increased, and the stability is improved.
While the present invention has been described in detail with reference to the preferred embodiments, it should be understood that the above description should not be taken as limiting the invention. Various modifications and alterations to this invention will become apparent to those skilled in the art upon reading the foregoing description. Within the technical idea of the invention, various equivalent changes can be made to the technical scheme of the invention, and the equivalent changes all belong to the protection scope of the invention.
Claims (4)
1. The utility model provides an adopt tail of series-parallel connection formula undercarriage to sit upright formula VTOL aircraft which characterized in that: the aircraft comprises an aircraft body (1), wings (2), a power system (3), a series two-section undercarriage (4) and a parallel two-degree-of-freedom undercarriage (5);
the tandem type two-section undercarriage (4) and the parallel type two-degree-of-freedom undercarriage (5) are symmetrically arranged on the upper side and the lower side of the wing (2), and the tandem type two-section undercarriage (4) and the parallel type two-degree-of-freedom undercarriage (5) are divided into two single groups and symmetrically arranged on the wing (2) on the left side and the right side of the fuselage (1);
the single group of the tandem type two-section landing gear (4) comprises a first support rod control system (401), a first support rod (402), a first tail support rod control system (403) and a first tail support rod (404) which are sequentially hinged; the first supporting rod control system (401) is installed on one side of the wing (2), and the first supporting rod control system (401) and the first tail supporting rod control system (403) are used for adjusting the relative angle and the form between the tandem type two-section undercarriage (4) and the airplane body (1);
the single group of the parallel two-degree-of-freedom undercarriage (5) comprises a second supporting rod control system (501), two second supporting rods (502), two second tail supporting rod control systems (503), two second tail supporting rods (504), a tail supporting vertical tail wing (505) and a tail supporting horizontal tail wing (506), wherein the second supporting rod control system (501) is installed on the other side of the wing (2), the top ends of the two second supporting rods (502) are hinged with the wing (2) through the second supporting rod control system (501), the tail ends of the two second supporting rods (502) are respectively provided with the second tail supporting rod control systems (503), the top ends of the two second tail supporting rods (504) are respectively hinged with the tail end of the second supporting rod (502) through the second tail supporting rod control system (503), the tail ends of the two second tail supporting rods (504) are hinged and provided with the tail supporting vertical tail wing (505), and the tail supporting horizontal tail wing (506) is installed between the tail supporting vertical tail wings (505) on the left side and the right side of the fuselage (1) The second supporting rod control system (501) and the second tail supporting rod control system (503) are used for adjusting the relative angle and the form between the parallel two-degree-of-freedom undercarriage (5) and the airplane body (1).
2. The aircraft adopting the series-parallel combined landing gear for the vertical take-off and landing on the tail of the aircraft as claimed in claim 1, wherein: and the wings (2) are provided with ailerons (6).
3. The aircraft adopting the series-parallel combined landing gear for the vertical take-off and landing on the tail of the aircraft as claimed in claim 1, wherein: the airplane wheel (7) is connected with the tail end of the second tail stay bar (504) and symmetrically arranged on the left side and the right side of the vertical tail wing (505) of the tail stay.
4. The aircraft adopting the series-parallel combined landing gear for the vertical take-off and landing on the tail of the aircraft as claimed in claim 1, wherein: the aircraft is characterized in that the first supporting rod control system (401), the first tail supporting rod control system (403), the second supporting rod control system (501) and the second tail supporting rod control system (503) are all provided with a single chip microcomputer, the single chip microcomputer is in wireless connection with the laser ranging unit and the inertia measurement unit, and the laser ranging unit and the inertia measurement unit are arranged on the wings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110612864.9A CN113232840B (en) | 2021-06-02 | 2021-06-02 | Tail-sitting vertical type vertical take-off and landing aircraft adopting series-parallel landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110612864.9A CN113232840B (en) | 2021-06-02 | 2021-06-02 | Tail-sitting vertical type vertical take-off and landing aircraft adopting series-parallel landing gear |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113232840A CN113232840A (en) | 2021-08-10 |
| CN113232840B true CN113232840B (en) | 2022-04-22 |
Family
ID=77136541
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110612864.9A Active CN113232840B (en) | 2021-06-02 | 2021-06-02 | Tail-sitting vertical type vertical take-off and landing aircraft adopting series-parallel landing gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113232840B (en) |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103287576A (en) * | 2013-05-24 | 2013-09-11 | 北京航空航天大学 | Tailless layout single tail seat type vertical take-off and landing aircraft |
| US9731816B2 (en) * | 2014-12-08 | 2017-08-15 | The Boeing Company | Multi-position landing gear |
| CN107336826B (en) * | 2017-06-30 | 2023-08-15 | 浙江大学 | Many rotor folding unmanned aerial vehicle |
| CN107672803A (en) * | 2017-09-14 | 2018-02-09 | 青岛四合信息科技有限公司 | A kind of technology and device of the automatic detection calibration radio guard of unmanned plane |
| CN213109770U (en) * | 2020-06-18 | 2021-05-04 | 武汉捷讯无人机科技有限公司 | Foldable undercarriage of unmanned aerial vehicle |
-
2021
- 2021-06-02 CN CN202110612864.9A patent/CN113232840B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN113232840A (en) | 2021-08-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9254916B2 (en) | Vertical take-off and landing aircraft with tiltrotor power for use on land and in air | |
| CN107757273B (en) | Flying automobile | |
| CN103587683A (en) | Small-sized aircraft with tiltable rotor wings | |
| CN110914148A (en) | STOL aircraft | |
| CN106240814A (en) | A kind of power-controlled tail sitting posture mixed layout vertically taking off and landing flyer | |
| CN110834722A (en) | Self-adaptive landing device for multi-rotor unmanned aerial vehicle | |
| CN204173155U (en) | A kind of delta-wing aircraft | |
| US11820503B2 (en) | Aircraft having a folding system | |
| CN100358776C (en) | Miniature airplane pitch operating method and control mechanism | |
| CN112896499A (en) | Vertical take-off and landing aircraft with combined layout of tilting duct and fixed propeller | |
| CN104260873B (en) | A kind of delta-wing aircraft | |
| CN115158654A (en) | Rhombic composite wing aircraft | |
| CN113232840B (en) | Tail-sitting vertical type vertical take-off and landing aircraft adopting series-parallel landing gear | |
| CN112722263A (en) | Vertical/short-distance take-off and landing aircraft with distributed power coupling lift-increasing wing surfaces | |
| CN110217391B (en) | Oil-electricity hybrid power vertical take-off and landing forward-swept fixed wing unmanned aerial vehicle | |
| CN110281719A (en) | Flight vehicle and its mode conversion method | |
| CN113291460B (en) | Short-distance/vertical take-off and landing aircraft adopting variant landing gear | |
| CN100363232C (en) | Anti-bump device for passenger plane of civil aviation | |
| CN113415406A (en) | Wing interval adjusting module, aircraft comprising same and aircraft control method | |
| CN112896500A (en) | Aircraft with four ducts in tilting layout | |
| CN218858726U (en) | Unmanned aerial vehicle with parallel double rotor wing tailstocks | |
| CN109263916A (en) | A kind of aircraft | |
| CN113232838B (en) | Vertical take-off and landing aircraft with vertical tail seat based on dual-mode variant landing gear | |
| CN112319790B (en) | Aerodynamic layout structure of long-endurance aircraft integrating multiple rotors and fixed wings and control method thereof | |
| CN219115711U (en) | Single aircraft capable of taking off and landing vertically for long endurance |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |